IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0705691
(2010-02-15)
|
등록번호 |
US-8333348
(2012-12-18)
|
발명자
/ 주소 |
|
출원인 / 주소 |
|
인용정보 |
피인용 횟수 :
9 인용 특허 :
4 |
초록
▼
The disclosure provides in one embodiment a wing tip device for a wing of an air vehicle. The device comprises a tip tail element, a boom element attaching the tip tail element to a wing tip, a hinge element connecting the tip tail element to the boom element, and an actuator element connected to th
The disclosure provides in one embodiment a wing tip device for a wing of an air vehicle. The device comprises a tip tail element, a boom element attaching the tip tail element to a wing tip, a hinge element connecting the tip tail element to the boom element, and an actuator element connected to the hinge element. One or more wing load sensors sense wing loads, and a flight control system controls the actuator element. A load alleviation method and system for an air vehicle are also provided.
대표청구항
▼
1. A wing tip device for a wing of an air vehicle, the device comprising: a tip tail element;a boom element attaching the tip tail element to a wing tip, the boom element positioned inboard of the wing tip, the wing tip being at a terminal outer end of the wing;a hinge element connecting the tip tai
1. A wing tip device for a wing of an air vehicle, the device comprising: a tip tail element;a boom element attaching the tip tail element to a wing tip, the boom element positioned inboard of the wing tip, the wing tip being at a terminal outer end of the wing;a hinge element connecting the tip tail element to the boom element; and,an actuator element connected to the hinge element, wherein one or more wing load sensors sense wing loads, and further wherein a flight control system controls the actuator element. 2. The device of claim 1 wherein the device reduces wing loads and wing bending moments on the wing. 3. The device of claim 1 wherein the one or more wing load sensors sense wing loads and wing bending moments for use in the flight control system to determine a magnitude at which the wing is being loaded. 4. The device of claim 1 wherein the flight control system controls and commands the actuator element to actuate the hinge element and rotate the tip tail element about the boom element. 5. The device of claim 1 wherein the tip tail element extends outboard and aft of the wing tip, the tip tail element having an inboard end that lies within an elevation plane of a wing tip trailing vortex, resulting in a reduced net drag-due-to-lift of a combined load of the wing and the wing tip device. 6. The device of claim 1 wherein the tip tail element is movable and the actuator element is a linear actuator that rotates about the hinge element. 7. The device of claim 1 wherein the actuator element actively controls an angle of attack of the tip tail element relative to existing air flow conditions. 8. The device of claim 1 wherein the wing tip device can operate on a stalled wing. 9. The device of claim 1 wherein the wing tip device, when controlled by the flight control system, provides at least approximately 50% active reduction in wing loads and wing bending moments on the wing and at least approximately 15% passive reduction in wing loads and wing bending moments on the wing. 10. An air vehicle comprising: at least one fuselage;at least one wing having at least one wing tip;a flight control system;a power system;one or more wing load sensors connected to the flight control system and connected to the power system and used to sense wing loads and wing bending moments; and,a wing tip load alleviation device attached to the at least one wing tip, the device comprising: a tip tail element;a boom element attaching the tip tail element to the wing tip, the boom element positioned inboard of the wing tip, the wing tip being at a terminal outer end of the wing;a hinge element connecting the tip tail element to the boom element; and,an actuator element connected to the hinge element, wherein the flight control system controls the actuator element. 11. The air vehicle of claim 10 wherein the wing tip load alleviation device reduces wing loads and wing bending moments on the wing. 12. The air vehicle of claim 10 wherein the flight control system controls and commands the actuator element to actuate the hinge element and rotate the tip tail element about the boom element. 13. The air vehicle of claim 10 wherein during flight the wing tip load alleviation device flies at a lower lift coefficient than the wing, resulting in an increased stall margin when a wind gust load increases a wing angle of attack. 14. The air vehicle of claim 10 wherein the wing tip load alleviation device, when controlled by the flight control system, provides at least approximately 50% active reduction in wing loads and wing bending moments on the wing and at least approximately 15% passive reduction in wing loads and wing bending moments on the wing. 15. The air vehicle of claim 10 wherein the flight control system has one or more control algorithms that use the one or more wing load sensors to determine a magnitude at which the wing is being loaded. 16. A load alleviation method for use with a wing of an air vehicle, the method comprising: attaching a wing tip device to at least one wing tip of the wing of the air vehicle, the wing tip device comprising: a tip tail element;a boom element attaching the tip tail element to the wing tip, the boom element positioned inboard of the wing tip, the wing tip being at a terminal outer end of the wing;a hinge element connecting the tip tail element to the boom element; and,an actuator element connected to the hinge element; and,using a flight control system to control and command the actuator element to actuate the hinge element and rotate the tip tail element about the boom element. 17. The method of claim 16 wherein the wing tip device actively controls and reduces wing loads and wing bending moments on the wing of the air vehicle. 18. The method of claim 16 wherein the flight control system has one or more control algorithms that use one or more wing load sensors to determine a magnitude at which the wing is being loaded. 19. The method of claim 16 wherein the wing tip device, when controlled by the flight control system, provides at least approximately 50% active reduction in wing loads and wing bending moments on the wing and at least approximately 15% passive reduction in wing loads and wing bending moments on the wing. 20. The method of claim 16 further comprising operating the wing tip device on a stalled wing. 21. The method of claim 16 wherein the tip tail element is movable and the actuator element is a linear actuator that rotates about the hinge element. 22. The method of claim 16 wherein the tip tail element extends outboard and aft of the wing tip, the tip tail element having an inboard end that lies within an elevation plane of a wing tip trailing vortex, resulting in a reduced net drag-due-to-lift of a combined load of the wing and the wing tip device. 23. A load alleviation system for an air vehicle, the system comprising: a power system;a flight control system; and,a wing tip load alleviation device attached to at least one wing tip of a wing of the air vehicle, the device comprising: a tip tail element;a boom element attaching the tip tail element to the wing tip, the boom element positioned inboard of the wing tip, the wing tip being at a terminal outer end of the wing;a hinge element connecting the tip tail element to the boom element; and,an actuator element connected to the hinge element, wherein one or more wing load sensors sense wing loads, and further wherein the flight control system controls the actuator element. 24. The system of claim 23 wherein the wing tip load alleviation device reduces wing loads and wing bending moments on the wing. 25. The system of claim 23 wherein the flight control system comprises an air vehicle outer loop controller, an air vehicle controller, one or more flight sensors that sense air data, one or more control algorithms, and a load alleviation control system. 26. The system of claim 25 wherein the load alleviation control system comprises a load alleviation controller and the one or more wing load sensors that sense wing loads and wing deflections on the wing of the air vehicle. 27. The system of claim 26 wherein the load alleviation controller controls wing loads and wing deflections by commanding actuation of the tip tail element relative to the wing load sensors, resulting in alleviation of wing loads and wing deflections on the wing of the air vehicle. 28. The system of claim 26 wherein the load alleviation controller controls the wing tip load alleviation device to provide at least approximately 50% active reduction in wing loads and wing deflections on the wing and at least approximately 15% passive reduction in wing loads and wing deflections on the wing. 29. The system of claim 23 wherein the one or more wing load sensors sense wing loads and wing bending moments for use in the flight control system to determine a magnitude at which the wing is being loaded. 30. The system of claim 23 wherein the flight control system controls and commands the actuator element to actuate the hinge element and rotate the tip tail element about the boom element. 31. The system of claim 23 wherein the tip tail element is movable and the actuator element is a linear actuator that rotates about the hinge element. 32. The system of claim 23 wherein the system can be implemented to operate on a stalled wing.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.